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Analyse any airfoil from UIUC database in xfoil and obtain results.

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Airfoil_Analysis

This python code is developed by Sreemannarayana Ikkurthi, as a part of course notes for the course 15AES302: Aerodynamics II, in the year 2019-20

In support of Dr. Rajesh Senthil Kumar T., Assistant Professor,

Department of Aerospace Engneering, Amrita Vishwa Vidyapeetham.

Analyse any airfoil from UIUC database in xfoil and obtain cp and polar values

The Super_xfoil folder is the python module for finding cp and polar values for different flow parameters

Database folder consists of all the airfoils in UIUC airfoil data files in .dat or .DAT format.

Create a Results folder, it consists of all the output files from xfoil.

Xfoil folder consists of xfoil program.

Example.ipynb demonstrates some example functions of Super_xfoil

Source code info

The code consists of a class and several functions for analysing an airfoil in xfoil program.

The code by default selects a random airfoil from the UIUC database and apply spline to upper and lower surface of airfoil and produce required number of points for analysis. These new coordinates are analysed in xfoil with the given input variables.

The INPUTS section contains pts, Re, Mach, N_crit, Alpha variables

       pts = No. of points for spline

       Re =  Reynolds number

       Mach = Mach number

       N_crit =  Critical boundary layer interaction

       Alpha = Angle of attack
       
       database_path = path to database folder
       
       xfoil_path = path to xfoil folder

       results_path = path to results folder

       code_path = path to jupyter notebook file

If any specific airfoil is to be analysed then it can be entered to foil variable in THE CODE section.